Tandem rotors
Tandem rotor helicopters have two large horizontal rotor assemblies mounted one in front of the other. Currently this configuration is mainly used for large cargo helicopters.[1]
Single rotor helicopters need a mechanism to neutralize the yawing movement produced by the single large rotor. This is commonly accomplished by a tail rotor, coaxial rotors, and recently the NOTAR systems. Tandem rotor helicopters, however, use counter-rotating rotors, with each canceling out the other's torque. Therefore all of the power from the engines can be used for lift (force), whereas a single rotor helicopter uses some of the engine power to counter the torque.[1] An alternative is to mount two rotors in a coaxial configuration.
Advantages of the tandem-rotor system are a larger Center of gravity of an aircraft range and good longitudinal stability. Disadvantages of the tandem-rotor system are a complex transmission (mechanics),[1] and the need for two large rotors.
The two rotors are linked by a transmission that ensures the rotors are synchronized and do not hit each other, even during an engine failure.[2]
Tandem rotor designs achieve yaw by applying opposite left and right cyclic to each rotor, effectively pulling both ends of the helicopter in opposite directions. To achieve pitch, opposite collective is applied to each rotor; decreasing the lift produced at one end, while increasing lift at the opposite end, effectively tilting the helicopter forward or back.[3]
Tandem rotor aerodynamics is a complex subject.[citation needed] Tandem rotor helicopters have the advantage of being able to hold more weight with shorter blades, since there are two sets. However, the rear rotor works in the aerodynamic shadow of the front rotor, which reduces its efficiency. This loss can be minimized by increasing the distance between the two rotor hubs, and by elevating one hub over the other.[4][5] Tandem rotor helicopters tend to have a lower disk loading than single rotor helicopters.[6]
Tandem rotor helicopters typically require less power to hover and achieve low speed flight as compared to single rotor helicopters. Both configurations typically require the same power to achieve high speed flight.[7]
List of some tandem rotor helicopters
- HRP Rescuer (1945)
- Piasecki PV-14 (1948)
- HERC Jov-3 (1948)
- Piasecki H-21 (1949)
- McCulloch MC-4 (1951)
- Chu CJC-3, Taiwanese prototype helicopter with 190HP engine (1952)
- Piasecki H-25/HUP Retriever (1952)
- Yakovlev Yak-24 (1952)
- Bristol Belvedere (1952)
- Piasecki H-16 (1953)
- Bell HSL (1953)
- Boeing Vertol 107-II (1958)
- CH-46 Sea Knight (1960)
- CH-47 Chinook (1961)
- Jovair Sedan 4A (1963)
- Filper Beta 200 (1966)
- Filper Beta 400 (1967)
- Boeing Vertol XCH-62 (1970s - not completed)
- Boeing Model 234 (1981)
- Boeing Model 360 (1987)
See also
References
- ↑ 1.0 1.1 1.2 http://www.cavalrypilot.com/fm1-514/Ch3.htm
- ↑ Art of the helicopter by John Watkinson, p. 13
- ↑ http://www.helicopterpage.com/html/tandem.html
- ↑ Principles of helicopter aerodynamics by J. Gordon Leishman p. 73.
- ↑ Rotary Wing Aerodynamics, W.Z. Stepniewski, p. 197.
- ↑ Rotary Wing Aerodynamics, W.Z. Stepniewski, p. 185
- ↑ Rotary Wing Aerodynamics, W.Z. Stepniewski, p. 200.
